CN215949932U - High-pressure compressor rotor, aircraft engine and aircraft - Google Patents
High-pressure compressor rotor, aircraft engine and aircraft Download PDFInfo
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- CN215949932U CN215949932U CN202121114062.7U CN202121114062U CN215949932U CN 215949932 U CN215949932 U CN 215949932U CN 202121114062 U CN202121114062 U CN 202121114062U CN 215949932 U CN215949932 U CN 215949932U
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- pressure compressor
- compressor rotor
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Abstract
The utility model discloses a high-pressure compressor rotor, an aircraft engine and an aircraft, wherein the high-pressure compressor rotor comprises a rotor main body and a plurality of blades, the rotor main body comprises a first cylinder part, a drum type part and a second cylinder part, two ends of the drum type part are respectively connected to the first cylinder part and the second cylinder part, the plurality of blades are all connected to the outer peripheral surface of the drum type part, and the first cylinder part, the drum type part, the second cylinder part and the plurality of blades are integrally formed. The aircraft engine comprises a high-pressure compressor rotor as described above. The aircraft comprises an aircraft engine as described above. The high-pressure compressor rotor adopts the integrated design and manufacturing technical concept, the original part assembly is changed into the structure form of integrally designing a part, the structure is simplified, the weight is reduced, the assembly difficulty is reduced, the efficiency of the compressor is improved, and the fuel consumption is reduced.
Description
Technical Field
The utility model relates to a high-pressure compressor rotor, an aircraft engine and an aircraft.
Background
The aircraft engine has the advantages of complex structure, various parts, high part processing and manufacturing precision and great assembly difficulty of parts and the whole engine. At present, as shown in fig. 1, a high-pressure compressor rotor of an aircraft engine with a conventional configuration is complex, and generally comprises a front shaft neck, a stepped disc, blades, a locking block, a connecting bolt, a labyrinth disc and the like, so that the weight of the whole aircraft is high due to a large number of parts, the thrust-weight ratio is greatly limited to be further improved, and meanwhile, the reliability of the whole aircraft is poor, the assembly difficulty is high, and the efficiency is limited to be further improved due to a large number of parts.
SUMMERY OF THE UTILITY MODEL
The utility model provides a high-pressure compressor rotor, an aero-engine and an aircraft, aiming at overcoming the defects that the weight of the whole aircraft is high due to the fact that a plurality of high-pressure compressor rotor parts exist in the conventional aero-engine, the thrust-weight ratio is greatly limited, the reliability of the whole aircraft is poor, the assembly difficulty is high, and the efficiency is limited.
The utility model solves the technical problems through the following technical scheme:
the rotor of the high-pressure compressor is characterized by comprising a rotor main body and a plurality of blades, wherein the rotor main body comprises a first cylinder part, a drum type part and a second cylinder part, two ends of the drum type part are respectively connected to the first cylinder part and the second cylinder part, the plurality of blades are connected to the outer peripheral surface of the drum type part, and the first cylinder part, the drum type part, the second cylinder part and the plurality of blades are integrally formed.
In the scheme, the structural form is adopted, so that the high-pressure compressor rotor adopts an integrated design and manufacturing technical idea, the original part assembly is changed into an integrated design to be a structural form of one part, small parts such as a locking block, a check ring, a connecting bolt, a nut and the like of the high-pressure compressor rotor in the prior art are eliminated, the structure of the high-pressure compressor rotor is simplified, the types of the parts are reduced, the number of the parts is reduced from hundreds to 1, the configuration management difficulty is reduced, the structure is simplified, and the weight is reduced. Compared with the prior art that the requirement on the machining precision of a plurality of single pieces is high, the machining difficulty is generally reduced. The integrated design does not need to consider the concentricity problem, does not need single piece assembly, and reduces the assembly difficulty. Due to the adoption of the integrated design, the clearance between parts is eliminated, the aerodynamic loss is reduced, the efficiency is improved, the centrifugal force problem of the blades is eliminated, the rigidity of the high-pressure compressor rotor is improved, and the fuel consumption is reduced. Meanwhile, the whole high-pressure compressor rotor is a part, the whole structure is properly reinforced, and the safety and stability of the high-pressure compressor rotor are improved.
Preferably, the first cylinder part has a first sealing portion on an outer peripheral surface thereof.
In the scheme, by adopting the structure form, the first sealing part is mainly used for sealing, so that the sealing effect is greatly improved; meanwhile, the first sealing part is integrated on the rotor main body, so that the overall structure is more compact, the processing difficulty is reduced, the qualification rate is improved, and the assembling difficulty is reduced.
Preferably, the first sealing part is a labyrinth seal, a graphite seal, a brush seal or a piston ring seal.
Preferably, the inner wall surface of the first tubular member has an internal thread, a shoulder, and a second seal portion provided in this order in a direction close to the drum member.
In this scheme, adopt above-mentioned structural style, be used for installing fixing bearing through internal thread and shaft shoulder through the rotor main part, and then realize that the axial of high-pressure compressor rotor is spacing to reduce and improve the qualification rate, reduce the assembly degree of difficulty. Meanwhile, the second sealing part is matched with a labyrinth on the outer surface of the low-pressure turbine shaft in a sealing mode and the like, and the sealing device is mainly used for sealing between high-pressure rotors and low-pressure rotors, so that the sealing effect is greatly improved.
Preferably, the second sealing part is a coating.
Preferably, the inner wall surface of the second cylinder member has a fitting spigot.
In this scheme, adopt above-mentioned structural style, be used for mutually supporting and the tang centering with the high whirlpool through the cooperation tang, realize that the assembly precision is higher, reduce the assembly degree of difficulty.
Preferably, the outer circumferential surface of the drum member is uneven.
In this scheme, adopt above-mentioned structural style, rotor subject adopts the drum-type structure, and the prominent structural integrity to cancel the connecting piece, reduce weight, structural integrity is higher.
Preferably, the drum member has a cylindrical outer peripheral surface.
In this scheme, adopt above-mentioned structural style for the rotor main part processing degree of difficulty reduces to some extent on the whole, and the machining precision is higher.
An aircraft engine characterised in that it comprises a high-pressure compressor rotor as described above.
In the scheme, by adopting the structural form, the high-pressure compressor rotor adopts the integrated design and manufacturing technical idea, and the original part assembly is changed into the structural form of integrally designing the high-pressure compressor rotor into one part, so that the structure is simplified, the weight is reduced, the processing difficulty is reduced overall, the assembly difficulty is reduced, the efficiency is improved, and the fuel consumption of the aircraft engine is reduced. Meanwhile, the whole high-pressure compressor rotor is a part, the whole structure is properly reinforced, and the safety and stability of the aircraft engine are improved.
An aircraft characterised in that it comprises an aircraft engine as described above.
In the scheme, the structure is adopted, the integrated design and manufacturing technical concept is adopted for the high-pressure compressor rotor, the original part assembly is changed into the structure of integrally designing the high-pressure compressor rotor into one part, the structure is simplified, the weight is reduced, the processing difficulty is reduced overall, the assembly difficulty is reduced, the efficiency is improved, and the fuel consumption of the aircraft is reduced. Meanwhile, the whole high-pressure compressor rotor is a part, the whole structure is properly strengthened, and the safety and stability of the aircraft are improved.
On the basis of the common knowledge in the field, the above preferred conditions can be combined randomly to obtain the preferred embodiments of the utility model.
The positive progress effects of the utility model are as follows:
according to the high-pressure compressor rotor, the aircraft engine and the aircraft, the high-pressure compressor rotor adopts the integrated design and manufacturing technical concept, the original part assembly is changed into the structure form of integrally designing the high-pressure compressor rotor into one part, the structure is simplified, the weight is reduced, the assembly difficulty is reduced, the compressor efficiency is improved, and the fuel consumption is reduced.
Drawings
Fig. 1 is a schematic structural diagram of a high-pressure compressor rotor in the prior art.
Fig. 2 is a schematic view of the internal structure of a high-pressure compressor rotor according to embodiment 1 of the present invention.
Fig. 3 is a schematic view of the internal structure of a high-pressure compressor rotor according to embodiment 2 of the present invention.
Description of reference numerals:
rotor body 1
First sealing part 111
Shaft shoulder 113
Second tubular member 13
Detailed Description
The present invention will be more clearly and completely described below by way of examples and with reference to the accompanying drawings, but the present invention is not limited thereto.
Example 1
As shown in fig. 2, the high-pressure compressor rotor according to the embodiment of the present invention includes a rotor body 1 and a plurality of blades 2, the rotor body 1 includes a first cylinder part 11, a drum part 12, and a second cylinder part 13, both ends of the drum part 12 are respectively connected to the first cylinder part 11 and the second cylinder part 13, the plurality of blades 2 are connected to an outer circumferential surface of the drum part 12, and the first cylinder part 11, the drum part 12, the second cylinder part 13, and the plurality of blades 2 are integrally formed.
Through integrated into one piece between first section of thick bamboo part 11, drum-type part 12, second section of thick bamboo part 13 and a plurality of blade 2 for high-pressure compressor rotor adopts integrated design, the manufacturing technology theory, become the structural style of integrated design as a part by original part equipment, thereby small part such as the latch segment of high-pressure compressor rotor among the prior art, retaining ring, connecting bolt, nut has been cancelled, high-pressure compressor rotor's structure is simplified, the part kind reduces, reduce part quantity, part quantity is reduced to 1 by hundreds, the configuration management degree of difficulty reduces, realize that the structure is simplified, weight reduction. Compared with the prior art that the requirement on the machining precision of a plurality of single pieces is high, the machining difficulty is generally reduced. The integrated design does not need to consider the concentricity problem, does not need single piece assembly, and reduces the assembly difficulty. Due to the adoption of the integrated design, the clearance between parts is eliminated, the aerodynamic loss is reduced, the efficiency is improved, the centrifugal force problem of the blades is eliminated, the rigidity of the high-pressure compressor rotor is improved, and the fuel consumption is reduced. Meanwhile, the whole high-pressure compressor rotor is a part, the whole structure is properly reinforced, and the safety and stability of the high-pressure compressor rotor are improved.
The first cylindrical member 11 has a first seal portion 111 on its outer peripheral surface. The first sealing part 111 is mainly used for sealing, so that the sealing effect is greatly improved; meanwhile, the first sealing part 111 is integrated on the rotor main body 1, so that the overall structure is more compact, the processing difficulty is reduced, the qualification rate is improved, and the assembling difficulty is reduced. In this embodiment, the first sealing portion 111 is a labyrinth seal, a graphite seal, a brush seal or a piston ring seal. Of course, in other embodiments, the first sealing portion 111 may also be a graphite seal, a brush seal, or a piston ring seal. The first seal 111 includes, but is not limited to, a coating, a labyrinth, and the like.
The inner wall surface of the first cylindrical member 11 has an internal thread 112, a shoulder 113, and a second sealing portion 114 provided in this order in a direction toward the drum member 12. The rotor body 1 is used for installing and fixing a bearing through the internal thread 112 and the shaft shoulder 113, so that the axial limiting of the high-pressure compressor rotor is realized, the qualified rate is reduced, and the assembly difficulty is reduced. Meanwhile, the second sealing part 114 is matched with a labyrinth seal on the outer surface of the low-pressure turbine shaft and the like, and is mainly used for sealing between high-pressure rotors and low-pressure rotors, so that the sealing effect is greatly improved. In this embodiment, the second sealing portion 114 is a coating. Of course, in other embodiments, the second seal 114 includes, but is not limited to, a coating, a labyrinth, and the like.
The inner wall surface of the second cylindrical member 13 has an engagement spigot 131. Be used for mutually supporting and the tang centering with the high whirlpool through cooperation tang 131, realize that the assembly precision is higher, reduce the assembly degree of difficulty.
In the present embodiment, the outer peripheral surface of the drum member 12 is uneven. Rotor body 1 adopts the drum-type structure, and the prominent structural integrity to cancel the connecting piece, reduce weight, structural integrity is higher.
The embodiment of the utility model also discloses an aircraft engine which comprises the high-pressure compressor rotor. By adopting the integrated design and manufacturing technical concept of the high-pressure compressor rotor, the original structural form that the parts are assembled into one part is changed into the integrated design, the structure is simplified, the weight is reduced, the processing difficulty is generally reduced, the assembly difficulty is reduced, the efficiency is improved, and the fuel consumption of the aircraft engine is reduced. Meanwhile, the whole high-pressure compressor rotor is a part, the whole structure is properly reinforced, and the safety and stability of the aircraft engine are improved.
The embodiment of the utility model also discloses an aircraft which comprises the aero-engine.
Example 2
As shown in fig. 3, the same parts of the high-pressure compressor rotor structure of the present embodiment as those of embodiment 1 are not repeated, and only the differences will be described. In example 2, the outer peripheral surface of the drum member 12 is cylindrical. The processing difficulty of the rotor body 1 is reduced overall, and the processing precision is higher.
While specific embodiments of the utility model have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the utility model is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the utility model, and these changes and modifications are within the scope of the utility model.
Claims (10)
1. The high-pressure compressor rotor is characterized by comprising a rotor main body and a plurality of blades, wherein the rotor main body comprises a first cylinder part, a drum type part and a second cylinder part, two ends of the drum type part are respectively connected to the first cylinder part and the second cylinder part, the plurality of blades are connected to the outer peripheral surface of the drum type part, and the first cylinder part, the drum type part, the second cylinder part and the plurality of blades are integrally formed.
2. The high pressure compressor rotor as recited in claim 1, wherein the first barrel part has a first seal portion on an outer peripheral surface thereof.
3. The high pressure compressor rotor as recited in claim 2, wherein the first seal is a labyrinth seal, a graphite seal, a brush seal or a piston ring seal.
4. The high-pressure compressor rotor as claimed in claim 1, wherein the inner wall surface of the first cylinder member has an internal thread, a shoulder, and a second seal portion arranged in this order in a direction close to the drum member.
5. The high pressure compressor rotor as recited in claim 4, wherein the second seal is a coating.
6. The high pressure compressor rotor as recited in claim 1, wherein an inner wall surface of the second cylinder member has a mating spigot.
7. The high pressure compressor rotor as recited in claim 1, wherein the outer peripheral surface of the drum member is roughened.
8. The high-pressure compressor rotor as claimed in claim 1, characterized in that the outer circumferential surface of the drum member is cylindrical in shape.
9. An aircraft engine, characterized in that it comprises a high-pressure compressor rotor according to any one of claims 1 to 8.
10. An aircraft, characterized in that it comprises an aircraft engine according to claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121114062.7U CN215949932U (en) | 2021-05-21 | 2021-05-21 | High-pressure compressor rotor, aircraft engine and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121114062.7U CN215949932U (en) | 2021-05-21 | 2021-05-21 | High-pressure compressor rotor, aircraft engine and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215949932U true CN215949932U (en) | 2022-03-04 |
Family
ID=80565096
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121114062.7U Active CN215949932U (en) | 2021-05-21 | 2021-05-21 | High-pressure compressor rotor, aircraft engine and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215949932U (en) |
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2021
- 2021-05-21 CN CN202121114062.7U patent/CN215949932U/en active Active
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